Similarly shaped airfoils to GA 35-317
New! Bulk download of polars in Excel format: GA%2035-317.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA63-417 a=0.5
3. NACA63-417 a=0.6
4. NACA64-417 a=0.6
5. NACA64-417 a=0.5
6. NACA63-517
7. NACA63-417 a=0.8
8. NACA64-517
9. GA 35-316
10. GA 35-318
11. NACA64-417 a=0.8
12. GA 37-316
13. NACA63-418 a=0.6
14. NACA63-416 a=0.5
15. NACA63-418 a=0.5
16. NACA63-416 a=0.6
17. NACA63-517 a=0.2
18. GA 37-318
19. NACA63-517 a=0.0
20. NACA64-416 a=0.5
21. GA 35A317